Abstract: A solar array, comprising: at least one solar panel comprising a primary surface and a secondary surface; the primary surface having a group of direct solar cells disposed thereon, each of the direct solar cells configured to receive direct sunlight and to provide electrical power to a respective portion of a substantially flat flexible circuit; and the secondary surface having a group of indirect solar cells disposed thereon, each of the indirect solar cells configured to receive reflected sunlight and to provide electrical power to a respective portion of a substantially flat flexible circuit.

Abstract: Pipe elbows having an improved interior configuration for more smoothly turning the flow of fluids through the pipe elbow are disclosed. The pipe elbows have an intermediate portion joined to inlet and outlet portions between the inlet and outlet portions. The interior cross-section of the intermediate portion is in the configuration of a closed figure which has a first region between the centerline and the intrados and a second region between the centerline and the extrados in which the first region has a larger cross-sectional area than the second region. The configuration of the cross-sectional area of the intermediate portion is different from the configuration of the inlet and outlet portions.

Abstract: A deployable spacecraft element which has a solar energy collection and conversion means on one side of the deployable element and a radio frequency reflecting means on the other side of the deployable element. While the solar collection and conversion means and the radio frequency reflecting means are nominally oriented in opposite spatial directions and dependent on the orientation of the spacecraft to orient for solar collection or radio frequency transmission, one or more deployable elements may be mounted to a gimbal to allow for simultaneous solar collection and radio frequency collection by the spacecraft.

Abstract: A bidirectional regulating heat pipe network for a spacecraft payload temperature regulating system includes a payload having a thermal interface surfaces connected to a cool environment variable conductance heat pipe (CEVCHP) evaporator and a warm environment variable conductance heat pipe (WEVCHP) condenser to enable regulation of heat flow in or out of the payload in order to maintain a temperature within the payload's requirements.

Abstract: A system for managing propellant and pressurant for in-space propulsion of a spacecraft is provided. The system includes a conformal fuel tank having an ullage operatively connected for pressurization and a propellant management device (PMD) to wick propellant to a liquid port of the conformal fuel tank. The system further includes a pneumatic circuit including a tank pressurant vent valve for adjustment of operating pressure prior to refueling operations; a vent to release excess pressurant; a pressurant metering vent valve to provide control and safety relief for the pressurant; a check valve to prevent backflow; a pressurant cat bed for decomposing propellant into pressurant; a repressurizing valve to release pressurant once cooled; a burst disk to provide overpressure safety relief; a series of propellant extraction valves to intake a predetermined quantity of propellant for decomposition; and a pressure regulator that delivers proper pressure to a series of thrusters.

Abstract: Pipe elbows having an improved interior configuration for more smoothly turning the flow of fluids through the pipe elbow are disclosed. The pipe elbows have an intermediate portion joined to inlet and outlet portions between the inlet and outlet portions. The interior cross-section of the intermediate portion is in the configuration of a closed figure which has a first region between the centerline and the intrados and a second region between the centerline and the extrados in which the first region has a larger cross-sectional area than the second region. The configuration of the cross-sectional area of the intermediate portion is different from the configuration of the inlet and outlet portions.

Abstract: A thermomodulating heat pipe is provided including a heat pipe envelope having a capillary wick extending substantially continuously the full length of the heat pipe and a void space interior of the capillary wick. The heat pipe envelope has a nominal evaporator section, a nominal condenser section where the nominal condenser section includes an active condenser portion and an inactive condenser portion, and a reservoir section extending from the inactive condenser portion. At a nominal condition, a heat pipe fluid is provided with a liquid phase filling the capillary wick and a vapor phase filling the void space of the nominal evaporator section and the active condenser portion, a non-condensable gas filling the void space of at least the reservoir section and the inactive condenser portion. Depending on thermal conditions, both prograde and retrograde heat transfer are enabled.

Abstract: A ground testable spacecraft heat pipe has a spacecraft heat pipe thermally connected for conduction of heat through a heat acquisition cold plate to a heat acquisition riser of a bubble pump heat pipe, enabling a plug-slug flow of heated fluid into a separator, with heated liquid flowing downward through a hear rejection downcomer to a heat rejection pipe section mounted on a heat rejection cold plate for conduction of heat to a bottom end of the spacecraft heat pipe, the now-cooled liquid flowing through a heat rejection riser to an outlet in a condenser that receives the heated vapor from the separator through a vapor condensation conduit, the condenser holding the cooled fluid and vapor condensate that exits the condenser through a heat acquisition downcomer to restart the cycle.

Abstract: A deployable spacecraft element which has a solar energy collection and conversion means on one side of the deployable element and a radio frequency reflecting means on the other side of the deployable element. While the solar collection and conversion means and the radio frequency reflecting means are nominally oriented in opposite spatial directions and dependent on the orientation of the spacecraft to orient for solar collection or radio frequency transmission, one or more deployable elements may be mounted to a gimbal to allow for simultaneous solar collection and radio frequency collection by the spacecraft.

Abstract: A system for managing propellant and pressurant for in-space propulsion of a spacecraft is provided. The system includes a conformal fuel tank having an ullage operatively connected for pressurization and a propellant management device (PMD) to wick propellant to a liquid port of the conformal fuel tank. The system further includes a pneumatic circuit including a tank pressurant vent valve for adjustment of operating pressure prior to refueling operations; a vent to release excess pressurant; a pressurant metering vent valve to provide control and safety relief for the pressurant; a check valve to prevent backflow; a pressurant cat bed for decomposing propellant into pressurant; a repressurizing valve to release pressurant once cooled; a burst disk to provide overpressure safety relief; a series of propellant extraction valves to intake a predetermined quantity of propellant for decomposition; and a pressure regulator that delivers proper pressure to a series of thrusters.

Abstract: A deployable radiator panel system for a small spacecraft includes fusible metal thermal hinge having a hinge leaf affixed to a spacecraft fixed radiator panel and the corresponding hinge leaf affixed to a deployable radiator panel with fusible metal filling the interstices between knuckles of each leaf to provide a conductive heat transfer path from the spacecraft fixed radiator panel through its leaf to the intervening fusible metal and then to the deployable radiator panel leaf and finally to the deployable radiator panel. A method is provided to heat and melt the fusible metal, release the deployable radiator panel from a stowed position, apply torque to open the fusible thermal metal hinge and latch the deployable radiator panel in a deployed position, and cool and solidify fusible metal.